EP2660520A3 - Fuel/air premixing system for turbine engine - Google Patents

Fuel/air premixing system for turbine engine Download PDF

Info

Publication number
EP2660520A3
EP2660520A3 EP13165809.8A EP13165809A EP2660520A3 EP 2660520 A3 EP2660520 A3 EP 2660520A3 EP 13165809 A EP13165809 A EP 13165809A EP 2660520 A3 EP2660520 A3 EP 2660520A3
Authority
EP
European Patent Office
Prior art keywords
air
fuel
fuel nozzle
turbine engine
swirl
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13165809.8A
Other languages
German (de)
French (fr)
Other versions
EP2660520A2 (en
EP2660520B1 (en
Inventor
Baifang Zuo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2660520A2 publication Critical patent/EP2660520A2/en
Publication of EP2660520A3 publication Critical patent/EP2660520A3/en
Application granted granted Critical
Publication of EP2660520B1 publication Critical patent/EP2660520B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Abstract

A system includes a fuel nozzle. The fuel nozzle includes a center body configured to receive a first portion of air and to deliver the air to a combustion region. The fuel nozzle also includes a swirler (88) configured to receive a second portion of air and to deliver the air to the combustion region. The swirler includes an outer shroud wall (74), an inner hub wall (72), and a swirl vane (104). The swirl vane includes a radial swirl profile (130) at a downstream edge (128) of the swirl vane. The radial swirl profile includes a region extending from the outer shroud wall to a first transition point and a second region extending from the transition point to the inner hub wall. At least one of the first and second regions is substantially straight and at least one of the first and second regions is arcuate.
EP13165809.8A 2012-04-30 2013-04-29 Fuel/air premixing system for turbine engine Active EP2660520B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/460,700 US8925323B2 (en) 2012-04-30 2012-04-30 Fuel/air premixing system for turbine engine

Publications (3)

Publication Number Publication Date
EP2660520A2 EP2660520A2 (en) 2013-11-06
EP2660520A3 true EP2660520A3 (en) 2017-11-15
EP2660520B1 EP2660520B1 (en) 2022-06-08

Family

ID=48193154

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13165809.8A Active EP2660520B1 (en) 2012-04-30 2013-04-29 Fuel/air premixing system for turbine engine

Country Status (5)

Country Link
US (1) US8925323B2 (en)
EP (1) EP2660520B1 (en)
JP (1) JP6203530B2 (en)
CN (1) CN103375819B (en)
RU (1) RU2643908C2 (en)

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CN110848730A (en) * 2018-08-21 2020-02-28 通用电气公司 Flow control wall for a heat engine

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KR102116903B1 (en) * 2014-12-12 2020-05-29 한화에어로스페이스 주식회사 Swirler assembly
KR102050414B1 (en) * 2014-12-12 2019-11-29 한화에어로스페이스 주식회사 Swirler assembly
US11015809B2 (en) * 2014-12-30 2021-05-25 General Electric Company Pilot nozzle in gas turbine combustor
US20160186663A1 (en) * 2014-12-30 2016-06-30 General Electric Company Pilot nozzle in gas turbine combustor
US9939155B2 (en) * 2015-01-26 2018-04-10 Delavan Inc. Flexible swirlers
KR101884694B1 (en) 2015-05-27 2018-08-02 두산중공업 주식회사 Nozzle hub with fuel injection holes
KR101857786B1 (en) 2015-05-27 2018-05-15 두산중공업 주식회사 Fueling nozzles with advansed premixer.
US20170227225A1 (en) * 2016-02-09 2017-08-10 General Electric Company Fuel injectors and methods of fabricating same
US20170363294A1 (en) * 2016-06-21 2017-12-21 General Electric Company Pilot premix nozzle and fuel nozzle assembly
US10443854B2 (en) * 2016-06-21 2019-10-15 General Electric Company Pilot premix nozzle and fuel nozzle assembly
EP3301368A1 (en) * 2016-09-28 2018-04-04 Siemens Aktiengesellschaft Swirler, combustor assembly, and gas turbine with improved fuel/air mixing
CN106762225B (en) * 2016-11-22 2018-08-03 上海空间推进研究所 A kind of rocket engine anti-backfire nozzle
US20180216826A1 (en) * 2017-01-30 2018-08-02 Doosan Heavy Industries Construction Co., Ltd. Device to correct flow non-uniformity within a combustion system
KR101900192B1 (en) * 2017-04-27 2018-09-18 두산중공업 주식회사 Fuel nozzle assembly, fuel nozzle module and gas turbine engine having the same
KR102066042B1 (en) 2017-10-31 2020-01-14 두산중공업 주식회사 Combustor and gas turbine including the same
CN108443874B (en) * 2018-05-21 2024-03-22 温岭市博惠热能设备股份有限公司 Combustor and combustion head thereof
US10948188B2 (en) * 2018-12-12 2021-03-16 Solar Turbines Incorporated Fuel injector with perforated plate
KR102096580B1 (en) 2019-04-01 2020-04-03 두산중공업 주식회사 Combustion nozzle enhancing spatial uniformity of pre-mixture and gas turbine having the same
KR102197130B1 (en) * 2020-01-07 2020-12-31 두산중공업 주식회사 Combustor and gas turbine including the same
US11187414B2 (en) * 2020-03-31 2021-11-30 General Electric Company Fuel nozzle with improved swirler vane structure
CN111594872B (en) * 2020-04-13 2021-04-20 南京航空航天大学 Deformable swirler air flow distribution intelligent adjusting system and method
US11802693B2 (en) * 2021-04-16 2023-10-31 General Electric Company Combustor swirl vane apparatus
US11598526B2 (en) * 2021-04-16 2023-03-07 General Electric Company Combustor swirl vane apparatus
CN113091093A (en) * 2021-05-13 2021-07-09 中国联合重型燃气轮机技术有限公司 Air dome and nozzle for gas turbine
US20230212984A1 (en) * 2021-12-30 2023-07-06 General Electric Company Engine fuel nozzle and swirler

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110848730A (en) * 2018-08-21 2020-02-28 通用电气公司 Flow control wall for a heat engine
CN110848730B (en) * 2018-08-21 2022-02-18 通用电气公司 Flow control wall for a heat engine

Also Published As

Publication number Publication date
RU2013119487A (en) 2014-11-10
JP6203530B2 (en) 2017-09-27
CN103375819B (en) 2016-12-07
EP2660520A2 (en) 2013-11-06
JP2013231582A (en) 2013-11-14
EP2660520B1 (en) 2022-06-08
US8925323B2 (en) 2015-01-06
RU2643908C2 (en) 2018-02-06
US20130283805A1 (en) 2013-10-31
CN103375819A (en) 2013-10-30

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